Method and system for aiding the piloting of an aircraft, during a maneuver bringing about an increase in the attitude of the aircraft

ABSTRACT

A method of aiding the piloting of an aircraft during a maneuver, bringing about an increase in the attitude of the aircraft, is carried out automatically and repeatedly. According to the method, an attitude deviation is determined by subtracting a first value of attitude from a determined current attitude of the aircraft. A horizon line is presented on a display screen of a head-up display device, superimposed with the environment seen in front of the aircraft, as is an indication of the attitude deviation. The first value of attitude corresponds to the minimum value of (1) an optimal value of attitude at the end of the maneuver and (2) a value of attitude of protection against a rear collision.

FIELD OF THE INVENTION

The present invention relates to a method and a system for aiding thepiloting of an aircraft, during a maneuver bringing about an increase inthe attitude of the aircraft, for example during a rotation.

BACKGROUND OF THE RELATED ART

Within the framework of the present invention, rotation is understood tomean a maneuver of the aircraft, in particular of a transport aircraft,which brings about an increase in the angle of attitude during a takeoffphase. The present invention may also be applied to the followingmaneuvers: a go-around in the course of an approach phase or a flare-outduring a landing phase.

It is known that such a system for aiding piloting can comprise:

-   -   a set of information sources, including an information source        which determines a current attitude of the aircraft;    -   a calculation unit which is connected to said set of information        sources; and    -   a head-up display device of HUD type which is connected to said        calculation unit and which is able to present, on a display        screen, superimposed with the environment seen in front of the        aircraft, at least one attitude scale and a means of indication        (aircraft reference) associated with said attitude scale and        indicating said current attitude of the aircraft.

It is known to present, moreover, on said display screen, a markergenerally situated between +10° and +15° on the attitude scale, that thepilot will align with said aircraft reference so as to obtain, forexample in the case of a rotation, the desired attitude at the end ofrotation. This known way of providing information to the pilot hasseveral drawbacks. In particular:

-   -   the zone of the corresponding attitude scale being situated        outside the field of display when the aircraft exhibits a zero        attitude, the pilot does not see said marker at the moment of        the initiation of the rotation. This often induces an overshoot        of the desired value of attitude, by reason of too fast a        subsequent appearance of said marker in the field of display of        the display screen;    -   the pilot is compelled to look at the top part of the display        field so as to monitor the appearance of said marker, and this        may cause him to neglect the holding of the trajectory of the        aircraft on the center of the runway; and    -   the visual scan is hardly optimal. Specifically, the pilot first        looks downward during rolling, then upward during the rotation,        then again downward after the rotation (since he uses the speed        vector and the guidance associated therewith during the initial        climb).

SUMMARY OF THE INVENTION

The present invention relates to a method making it possible to remedythe aforesaid drawbacks.

For this purpose, according to the invention, said method is noteworthyin that the following steps are carried out automatically andrepeatedly:

-   a) a first value of attitude of the aircraft is taken into account;-   b) the current attitude of the aircraft is determined;-   c) an attitude deviation is determined by subtracting said first    value of attitude from said current attitude; and-   d) at least one horizon line and a first means of indication which    indicates said attitude deviation are presented on a display screen    of a head-up display device, superimposed with the environment seen    in front of the aircraft.

Thus, by virtue of its mode of determination, and as specifiedhereinbelow, said first means of indication is presented under saidhorizon line, that is to say in the zone (at the bottom) where thepilot's gaze normally falls when managing the lateral control of theaircraft.

Preferably, said first means of indication is presented on an attitudescale, on which is also presented a second means of indicationindicating said current attitude of the aircraft.

In a first embodiment, said first value of attitude corresponds to anoptimal value of attitude at the end of the maneuver, for example at theend of the rotation. Thus, in order for the aircraft to exhibit at theend of the maneuver said prescribed optimal value of attitude, itsuffices to make said first means of indication (indicating said optimalvalue of attitude) and said horizon line correspond. Furthermore,advantageously, in step d), a symbol of protection against a rearcollision (or “tailstrike”) is moreover presented on the display screen.

In a second embodiment, said first value of attitude corresponds to theminimum value between, on the one hand, an optimal value of attitude atthe end of the maneuver (which is in general constant) and, on the otherhand, a value of attitude of protection against a rear collision (whichis in general variable). Within the framework of the present invention,rear collision is understood to mean the collision of the tail of theaircraft with the ground when the attitude of the aircraft reaches toolarge a value.

Thus, this second embodiment integrates a rear collision preventionfunction, as specified hereinbelow.

Preferably, during a phase of takeoff of the aircraft, said minimumvalue corresponds:

-   -   to said value of attitude of protection, which is constant, when        the aircraft is rolling on the ground;    -   to said value of attitude of protection, which becomes variable        and increasing, when the main landing gear of the aircraft        leaves the ground, doing so until this value of attitude of        protection becomes equal to said optimal value of attitude; and    -   to said optimal value of attitude thereafter.

Furthermore, in a particular variant embodiment applied to the aforesaidfirst embodiment, said first means of indication is presented on saiddisplay screen at a fixed position and said horizon line is presented onsaid display screen in a moveable manner. Thus, the pilot must bringsaid moveable horizon line (by increasing the attitude of the aircraft)onto said first fixed means of indication, so as to perform the maneuverin such a way as to obtain said optimal value of attitude at the end ofthe maneuver.

The present invention makes it possible to solve the aforesaid variousproblems. Specifically:

-   -   said first means of indication remains permanently in the field        of display of the display screen, thereby enabling the pilot to        anticipate the stoppage of the attitude increase;    -   said first means of indication is displayed in the zone (on the        runway, hence under the horizon line) where the pilot's gaze        naturally falls when managing the lateral control of the        aircraft; and    -   monitoring is convenient and continuous, since the speed vector        (that the pilot follows during the initial climb) emerges from        the horizon.

Furthermore, as indicated previously, by virtue of the taking intoaccount in the second aforesaid embodiment of said value of attitudeprotection, (in the definition of said first means of indication), arear collision prevention function is moreover obtained.

The present invention also relates to a system for aiding piloting foran aircraft, said system comprising:

-   -   a set of information sources, comprising at least one        information source which determines a current attitude of the        aircraft;    -   a calculation unit which is connected to said set of information        sources; and    -   a head-up display device, which is connected to said calculation        unit and which is able to present, on a display screen,        superimposed with the environment seen in front of the aircraft,        at least one horizon line.

According to the invention:

-   -   said system furthermore comprises:        -   a first means for transmitting a first value of attitude;            and        -   a second means for determining an attitude deviation, by            subtracting said first value of attitude from said current            attitude; and    -   said display device moreover presents on said display screen,        superimposed with the environment seen in front of the aircraft,        at least one first means of indication indicating said attitude        deviation.

Advantageously, said display device is formed in such a way as tomoreover present, on said display screen, an attitude scale and a secondmeans of indication which is associated with said attitude scale andwhich indicates the current attitude of the aircraft.

In a particular embodiment, said system furthermore comprises a means ofinput making it possible for an operator to input (into said system) atleast one value liable to be transmitted as first value of attitude, andin particular said optimal value of attitude.

Furthermore, in a preferred embodiment making it possible to prevent anyrisk of rear collision, said first means is formed so as to (determineand) transmit to the second means, as first value of attitude, theminimum value between, on the one hand, an optimal value of attitude atthe end of the maneuver (for example at the end of the rotation) and, onthe other hand, a value of attitude of protection against a rearcollision.

The figures of the appended drawing will elucidate the manner in whichthe invention may be embodied. In these figures, identical referencesdesignate similar elements.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is the schematic diagram of a system for aiding piloting inaccordance with the invention.

FIG. 2 illustrates a display that can be implemented by a system foraiding piloting in accordance with the invention.

DETAILED DESCRIPTION OF THE INVENTION

The system 1 in accordance with the invention and representeddiagrammatically in FIG. 1 is intended to aid a pilot of an aircraft, inparticular a transport aircraft, to pilot said aircraft during amaneuver of the aircraft bringing about an increase in the angle ofattitude, in particular in the course of a rotation during a takeoffphase or else during a go-around or a flare-out during a landing phase.

To do this, said system 1 is of the type comprising:

-   -   a set 2 of information sources, comprising in particular an        information source which determines in standard fashion a        current attitude of the aircraft (not represented);    -   a calculation unit 3 which is connected by a link 4 to said set        2 of information sources; and    -   a head-up display device 5 of HUD type which is connected to        said calculation unit 3 by a link 6 and which is able to        present, on a standard transparent display screen 7,        superimposed with the environment seen in front of the aircraft,        at least one horizon line 10 and possibly a standard attitude        scale 8, as well as at least one standard means of indication 9        which indicates the current attitude of the aircraft on said        attitude scale 8, as represented in FIG. 2.

The aircraft exhibits a current attitude of value AO, namely nearly fivedegrees for the example represented in FIG. 2.

Furthermore, according to the invention:

-   -   said system 1 furthermore comprises:        -   a means 11 for transmitting a first value of attitude A1;            and        -   a means 12 connected by a link 13 to said means 11 for            determining an attitude deviation A2, by subtracting said            first value of attitude A1 from said current attitude A0            (that is to say A2=A0−A1); and    -   said display device 5 presents, moreover, on said display screen        7, superimposed with the environment seen in front of the        aircraft, a means of indication 14 which indicates said attitude        deviation A2 on said attitude scale 8.

In a preferred embodiment represented in FIG. 1, said means 11 and 12are integrated into the central unit 3.

In a first particular embodiment, said first value of attitude A1corresponds to an optimal value of attitude at the end of the maneuver,for example at the end of the rotation. It will be noted that theoptimal value of attitude to be reached at the end of the maneuverdepends on the aircraft and possibly even on the conditions on the day.By way of illustration, it may be 12.5° or 15°, at the end of therotation, for a slow and heavy tactical transport aircraft. Thus, inorder for the aircraft to exhibit at the end of the maneuver saidprescribed optimal value of attitude A1, it suffices to make said meansof indication 14 (indicating said attitude deviation A2) and saidhorizon line 10 correspond in such a way that at the end of therotation, the current attitude A0 of the aircraft is equal to said valueA1.

In this case, said means of indication 14 presents a fixed position onthe display screen 7 under said means of indication 9, at a distance(value of attitude A1) corresponding to the attitude to be reached atthe end of the rotation. The pilot must therefore bring the means ofindication 14 onto the horizon line 10 during the maneuver. For thispurpose, said means of indication 14 being fixed, the horizon line 10which is moveable descends into the field of display of the displayscreen 7 when the pilot increases in standard fashion the attitude ofthe aircraft.

In a preferred variant embodiment applied to said first embodiment:

-   -   said calculation unit 3 determines a safety margin A3 with        respect to a rear collision, that is to say with respect to a        collision of the tail of the aircraft with the ground when the        attitude of the aircraft reaches too large a value. This safety        margin A3 is equal to the difference between a protection        attitude A4 and the current attitude A0; and    -   said display device 5 moreover presents on the display screen 7        a corresponding protection symbol (not represented) illustrated        for example by a horizontal segment. This symbol of protection        against a rear collision is moveable and is presented above said        means of indication 14 which is fixed, at a distance        representative of said safety margin A3.

In the course of a rotation, the pilot brings the moveable horizon line10 onto the fixed means of indication 14, taking care to keep this meansof indication 14 under said protection symbol, so as to avoid a rearcollision (“tailstrike”).

By way of example, during a phase of takeoff of the aircraft,chronologically, said symbol of protection against a rear collision:

-   -   is initially fixed;    -   then descends with the horizon line 10 toward the means of        indication 14 at the moment of the rotation (since the current        attitude A0 increases progressively). The pilot takes care to        see that the means of indication 14 never passes above said        protection symbol, so as to avoid a rear collision; and    -   just after takeoff, climbs back up progressively toward the        horizon line 10 until it passes above, since the angle of        collision and thus the value of attitude of protection A4 which        depends thereon are increasing. The pilot can henceforth bring        the protection symbol 14 to the horizon, thereby bringing the        aircraft to the optimal attitude A1.

In a second particular embodiment, said first value of attitude A1corresponds to the minimum value between, on the one hand, an optimalvalue of attitude at the end of the rotation (as specified above) and,on the other hand, value of attitude of protection against a rearcollision, that is to say for protection against a collision of the tailof the aircraft with the ground when the attitude of the aircraftreaches too large a value.

Thus, this second embodiment directly integrates a rear collisionprevention function, as specified hereinbelow.

The value of attitude of protection is dependent, preferably, on anangle of collision which depends in particular on the height withrespect to the ground of the aircraft and:

-   -   which is minimal and constant, when the aircraft is on the        ground; and    -   which increases progressively after takeoff (instant at which        the main landing gear of the aircraft leaves the ground), until        the risk of rear collision no longer exists.

The value of this angle of collision (which corresponds to the angle ofattitude for which the aircraft touches the ground with its tail) andthe value of attitude of protection (which is preferably a few degreesless than said angle of collision) vary as a function of the height andof the attitude of the aircraft.

The set 2 of information sources comprises means which provide theactual height and the actual trim of the aircraft. In a firstembodiment, this information (height and trim) are provided to the means11 which calculates said protection value of attitude, while, in asecond embodiment, this information is provided to a means ofcalculation which also forms part of said set 2 of information sourcesand which is formed so as to calculate said value of attitude ofprotection and transmit it to said means 11.

Said means 11 also determines the minimum value (between said protectionvalue of attitude and the optimal value of attitude), which minimumvalue is transmitted to said means 12.

Preferably, during a phase of takeoff of the aircraft, said minimumvalue corresponds:

-   -   to said value of attitude of protection, which is constant, when        the aircraft is rolling on the ground;    -   to said value of attitude of protection, which becomes variable        and increasing, when the main landing gear of the aircraft        leaves the ground, doing so until this protection value of        attitude becomes equal to said optimal value of attitude; and    -   to said optimal value of attitude thereafter.

The system 1 in accordance with the invention furthermore comprises ameans of input 15, for example a keyboard, allowing an operator to inputinto said system 1 at least one value which is used by said central unit3 (and in particular by said means 11), and in particular said optimalvalue of attitude.

With this second embodiment, the pilot must therefore bring said horizonline 10 (by increasing the attitude of the aircraft) onto said means ofindication 14, so as to perform the rotation, in such a way as to obtainsaid optimal value of attitude at the end of the rotation. In this case,said means of indication 14 is only fixed before takeoff. Moreover, todo this, it is necessary to take care to see that said horizon line 10never passes under said means of indication 14, so as to avoid thecurrent attitude A0 of the aircraft overshooting said value of attitudeof protection A1, and thus to prevent any rear collision.

Thus, for example, for an aircraft for which the optimum value ofattitude at the end of the rotation is 15°, and for which the protectionvalue of attitude is initially 11°:

-   -   the symbol for aiding rotation (means of indication 14) is        initially displayed 11° under the aircraft reference (means of        indication 9);    -   the pilot increases the attitude during the rotation, this        having the effect of making the horizon line 10 which is        moveable approach said symbol for aiding rotation (means of        indication 14) which is fixed before takeoff. The pilot takes        care to see that the horizon line 10 never passes under said        symbol for aiding rotation (means of indication 14) so as to        avoid a rear collision;    -   just after takeoff, the angle of collision and hence the value        of attitude of protection which depends thereon increase        progressively, and the symbol for aiding rotation (means of        indication 14) descends henceforth progressively from the        position at 11° under the aircraft reference (means of        indication 9) to a position at 15° under the aircraft reference        (means of indication 9) where it stops;    -   the pilot continues to make the means of indication 14 approach        the horizon line 10, thereby bringing the aircraft to the        optimal attitude of 15°.

By reason of the standard rotation speeds (rate of increase of theattitude) and of the standard values of attitude during takeoff, thesequence described hereinabove runs in a continuous manner for the pilotwho maintains a quasi-continuous rate of rotation throughout therotation maneuver. The symbol for aiding rotation (means of indication14) therefore provides the pilot with:

-   -   a reference which aids him in perceiving his speed of rotation        while continuing to look at the runway (situated at the bottom        of the field of display of the display screen 7);    -   protection against a rear collision; and    -   a target value making it possible to reach the optimal attitude        at the end of the rotation.

1. A method of aiding the piloting of an aircraft during a maneuverbringing about an increase in the attitude of the aircraft, according towhich method the following steps are carried out automatically andrepeatedly: a) a first value of attitude of the aircraft is taken intoaccount; b) the current attitude of the aircraft is determined; c) anattitude deviation is determined by subtracting said first value ofattitude from said current attitude; and d) at least one horizon line ispresented on a display screen of a head-up display device, superimposedwith the environment seen in front of the aircraft, wherein: in step d),a first section of indication which indicates said attitude deviation ismoreover presented on said display screen, said first value of attitudecorresponds to an optimal value of attitude at the end of the maneuver,and said first section of indication is presented on said display screenat a fixed position and said horizon line is presented on said displayscreen in a moveable manner.
 2. The method as claimed in claim 1,wherein said first section of indication is presented on an attitudescale, on which is also presented a second section of indicationindicating said current attitude of the aircraft.
 3. The method asclaimed in claim 1, wherein in step d), a symbol of protection against arear collision is moreover presented on the display screen.
 4. Anaircraft, which comprises a system able to implement the methodspecified under claim
 1. 5. A method of aiding the piloting of anaircraft during a maneuver bringing about an increase in the attitude ofthe aircraft, according to which method the following steps are carriedout automatically and repeatedly: a) a first value of attitude of theaircraft is taken into account; b) the current attitude of the aircraftis determined; c) an attitude deviation is determined by subtractingsaid first value of attitude from said current attitude; and d) at leastone horizon line is presented on a display screen of a head-up displaydevice, superimposed with the environment seen in front of the aircraft,wherein: in step d), a first section of indication which indicates saidattitude deviation is moreover presented on said display screen, andsaid first value of attitude corresponds to the minimum value between,on the one hand, an optimal value of attitude at the end of the maneuverand, on the other hand, a value of attitude of protection against a rearcollision.
 6. The method as claimed in claim 5, wherein said firstsection of indication is presented on an attitude scale, on which isalso presented a second section of indication indicating said currentattitude of the aircraft.
 7. The method as claimed in claim 5, wherein,during a phase of takeoff of the aircraft, said minimum valuecorresponds: to said value of attitude of protection, which is constant,when the aircraft is rolling on the ground; to said value of attitude ofprotection, which becomes variable and increasing, when the main landinggear of the aircraft leaves the ground, doing so until this value ofattitude of protection becomes equal to the optimal value of attitude;and to said optimal value of attitude thereafter.
 8. A system for aidingpiloting for an aircraft, said system comprising: a set of informationsources, comprising at least one information source which determines acurrent attitude of the aircraft; a first section that transmits a firstvalue of attitude; a second section that determines an attitudedeviation, by subtracting said first value of attitude from said currentattitude; a calculation unit which is connected to said set ofinformation sources; and a head-up display device, which is connected tosaid calculation unit and which is able to present, on a display screen,superimposed with the environment seen in front of the aircraft, atleast one horizon line, wherein: said display device moreover presentson said display screen, superimposed with the environment seen in frontof the aircraft, at least one first section of indication indicatingsaid attitude deviation determined by said second section, and saidfirst section is formed so as to transmit, as the first value ofattitude, the minimum value between, on the one hand, an optimal valueof attitude at the end of the maneuver and, on the other hand, a valueof attitude of protection against a rear collision.
 9. The system asclaimed in claim 8, wherein said display device is formed in such a wayas to moreover present, on said display screen, an attitude scale and asecond section of indication which is associated with said attitudescale and which indicates the current attitude of the aircraft.
 10. Thesystem as claimed in claim 8, wherein it furthermore comprises a sectionof input making it possible for an operator to input at least one valuecorresponding to said optimal value of attitude.
 11. An aircraft, whichcomprises a system such as that specified under claim 8.